EP2690365B1 - Acoustic damper, combustor, and gas turbine - Google Patents
Acoustic damper, combustor, and gas turbine Download PDFInfo
- Publication number
- EP2690365B1 EP2690365B1 EP12760742.2A EP12760742A EP2690365B1 EP 2690365 B1 EP2690365 B1 EP 2690365B1 EP 12760742 A EP12760742 A EP 12760742A EP 2690365 B1 EP2690365 B1 EP 2690365B1
- Authority
- EP
- European Patent Office
- Prior art keywords
- acoustic
- partition member
- vibration
- combustor
- acoustic damper
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
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Links
- 238000005192 partition Methods 0.000 claims description 154
- 238000002485 combustion reaction Methods 0.000 claims description 39
- 239000007789 gas Substances 0.000 claims description 24
- 239000000567 combustion gas Substances 0.000 claims description 8
- 230000007704 transition Effects 0.000 description 54
- 230000001902 propagating effect Effects 0.000 description 18
- 238000010586 diagram Methods 0.000 description 12
- 239000000446 fuel Substances 0.000 description 9
- 238000006073 displacement reaction Methods 0.000 description 8
- 239000002737 fuel gas Substances 0.000 description 5
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 4
- 239000003546 flue gas Substances 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000013016 damping Methods 0.000 description 3
- 239000012530 fluid Substances 0.000 description 2
- 238000006243 chemical reaction Methods 0.000 description 1
- 239000000470 constituent Substances 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
Images
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01N—GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR MACHINES OR ENGINES IN GENERAL; GAS-FLOW SILENCERS OR EXHAUST APPARATUS FOR INTERNAL COMBUSTION ENGINES
- F01N13/00—Exhaust or silencing apparatus characterised by constructional features ; Exhaust or silencing apparatus, or parts thereof, having pertinent characteristics not provided for in, or of interest apart from, groups F01N1/00 - F01N5/00, F01N9/00, F01N11/00
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/16—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration with devices inside the flame tube or the combustion chamber to influence the air or gas flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/04—Antivibration arrangements
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/24—Heat or noise insulation
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23M—CASINGS, LININGS, WALLS OR DOORS SPECIALLY ADAPTED FOR COMBUSTION CHAMBERS, e.g. FIREBRIDGES; DEVICES FOR DEFLECTING AIR, FLAMES OR COMBUSTION PRODUCTS IN COMBUSTION CHAMBERS; SAFETY ARRANGEMENTS SPECIALLY ADAPTED FOR COMBUSTION APPARATUS; DETAILS OF COMBUSTION CHAMBERS, NOT OTHERWISE PROVIDED FOR
- F23M20/00—Details of combustion chambers, not otherwise provided for, e.g. means for storing heat from flames
- F23M20/005—Noise absorbing means
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/002—Wall structures
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/005—Combined with pressure or heat exchangers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
- F23R3/04—Air inlet arrangements
- F23R3/06—Arrangement of apertures along the flame tube
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2260/00—Function
- F05D2260/96—Preventing, counteracting or reducing vibration or noise
- F05D2260/964—Preventing, counteracting or reducing vibration or noise counteracting thermoacoustic noise
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
- F23R2900/03041—Effusion cooled combustion chamber walls or domes
Definitions
- the present invention relates to an acoustic damper, a combustor, and a gas turbine.
- a combustor in which a combustion chamber is provided with the acoustic damper according to the above aspect and air vibration of combustion gas flowing in the combustion chamber is allowed to flow in the acoustic damper.
- the air received from the air inlet 15 of the compressor 11 passes through the plurality of vanes 17 and blades 18 and is compressed to be high-temperature and high-pressure compressed air, and predetermined fuel is supplied to the compressed air and is burned in the combustor 12.
- the high-temperature and high-pressure combustion gas that is operation fluid generated by the combustor 12 passes through the plurality of vanes 21 and blades 22 constituting the turbine 13 to drive and rotate the rotor 24 and drive the electric generator connected to the rotor 24, and the flue gas is discharged to the air after conversion to positive pressure with the flue diffuser 23 of the flue chamber 14.
- the high-temperature and high-pressure air from the compressor 11 flows from the base end side of the inner cylinder 32 into the inner cylinder 32 through the cylinder 38.
- the compressed air is induced to the pilot nozzle 35 and the main nozzle 36.
- the compressed air is mixed with fuel ejected from the main nozzle 36 to be premixed gas, and the gas flows into the transition piece 33.
- the compressed air is mixed with fuel ejected from the pilot nozzle 35, is ignited and burned by pilot light (not illustrated) to be combustion gas, and the gas is ejected into the transition piece 33.
- the acoustic damper 1A is provided along the circumferential direction on the outer surface on the base end side of the transition piece 33 in the combustor 12.
- the acoustic damper 1A includes a housing 2 surrounding the outside of the transition piece 33 as the vibration source.
- the housing 2 includes a cylindrical outer wall portion 2a surrounding the outside of the transition piece 33 in the circumferential direction, and a side wall portion 2b fixed to the transition piece 33 while closing both openings of the outer wall portion 2a, and forms an annular space on the outside of the transition piece 33.
- a partition member 5b is provided in the middle between the inlet and the end portion of each passage R.
- the partition member 5b blocks the middle of the passage R.
- the space between the inlet thereof and the partition member 5b is configured as an acoustic portion N that reduces pressure fluctuation in the combustor 12 in the passage R.
- the acoustic portion N is configured in which the positions of the inlet and the partition member 5b in the circumferential direction are inverted.
- the air vibration (the pressure wave) V based on the combustion vibration of the combustion gas passes through the through-hole 33a of the transition piece 33 and is received in the housing 2.
- the air vibration V propagating from the inlet resonates, and the pressure fluctuation in the combustor 12 is reduced.
- the position in the circumferential direction between the inlet of each acoustic portion N and the partition member 5b is inverted, and thus the propagation direction of the air vibration V becomes the reverse direction.
- FIG. 6 is a schematic diagram illustrating that an acoustic damper compared with the acoustic damper according to the embodiment is developed in the circumferential direction
- FIG. 7 and FIG. 8 are diagrams illustrating an influence based on the acoustic damper of FIG. 6 .
- the position of the partition member 5b in the circumferential direction is a gap between the partition member 5b and the inlet, and determines the length of the acoustic portion N.
- the length of the acoustic portion N is a distance for resonating the propagating air vibration V, and the distance is determined according to the frequency of the propagating air vibration V. That is, the position of the partition member 5b in the circumferential direction is determined according to the frequency of the air vibration V that is a reducing target.
- the positions of the partition member 5c and the partition member 5b in the circumferential direction are a gap between the partition member 5b and the inlet, and determine the length of the acoustic portion N.
- the length of the acoustic portion N is a distance for reducing the propagating air vibration V, and the distance is determined according to the frequency of the propagating air vibration V. That is, the positions of the partition member 5c and the partition member 5b in the circumferential direction are determined according to the frequency of the air vibration V that is the reducing target.
- the propagating direction of the air vibration V is the reverse direction between the partition members 5d.
- the exciting force F occurring at the position of the partition member 5d on one direction side of the circumferential direction and the exciting force F occurring at the position of the partition member 5b on the other direction side of the circumferential direction act in the reverse direction to each other.
- the transition piece 33 of the combustor 12 the displacement occurring in the circumferential direction is suppressed.
- the acoustic portion N is provided along the outer surface of the vibration source, the passage R is provided to be folded, and thus it is possible to configure the acoustic dampers (1C and 1D) in a relatively compact size.
- the plurality of acoustic portions N are provided, and thus it is possible to reduce the air vibration V according to the plurality of frequencies of the air vibration V.
- the acoustic portion N is provided along the outer surface of the vibration source, the passage R is provided to be folded, and thus it is possible to configure the acoustic dampers (1B, 1C, and 1D) in a relatively compact size.
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Soundproofing, Sound Blocking, And Sound Damping (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Description
- The present invention relates to an acoustic damper, a combustor, and a gas turbine.
- In the related art, for example, in Patent Literature 1, in order to reduce vibration in a wide frequency band, an acoustic damper including a pipe line with a passage and including a resistor which applies resistance to a fluid flowing in the pipe line is disclosed. In the acoustic damper, the bent and small-sized pipe line and resistor are mounted on a bypass pipe mounted on a combustion chamber of a combustor, and the inside of the bypass pipe communicates with the inside of the pipe line through the passage of the pipe line.
- In addition, in the related art, for example, in
Patent Literature 2, in order to improve a damping performance and maintenance workability, a damping device including an acoustic liner including an acoustic liner resonance space including a porous plate and a housing, and an acoustic damper connected to the housing and including an acoustic damper resonance space communicating with the acoustic liner resonance space therein is disclosed. In the damping device, the acoustic liner is mounted in the vicinity of a transition piece of a combustor, and the acoustic damper is provided along an extending direction of the transition piece. An acoustic damper according to the preamble of claim 1 is known fromWO 2010/097982 A1 . -
- Patent Literature 1: Japanese Patent Laid-open No.
2006-22966 - Patent Literature 2: Japanese Patent Laid-open No.
2006-266671 - However, the acoustic damper is a kind of resonance box, and thus large pressure fluctuation occurs in the acoustic damper. When large stress occurs in the combustor by the pressure fluctuation, the combustor may be damaged. For this reason, in order not to transfer the large stress to the combustor, a configuration is necessary in which the acoustic damper and the combustor are not fixed to each other. For this reason, by separating the acoustic damper from the combustor, an installation space of the acoustic damper with respect to the combustor becomes wider, and there may be a case in which a space for installing the acoustic damper is not secured in a very small-sized combustor.
- The present invention has been made to solve the problem described above, an object of the invention is to provide an acoustic damper, a combustor, and a gas turbine capable of preventing generation of stress due to pressure fluctuation caused when reducing vibration and of achieving a relatively compact configuration.
- According to an aspect of the present invention in order to achieve the object, there is provided an acoustic damper according to claim 1.
- According to the acoustic damper, the pressure fluctuation in the vibration source is reduced by the acoustic portion. In addition, the exciting force generated by collision of the air vibration to the partition member when reducing the pressure fluctuation is suppressed with each other by each partition member serving as resistance of the air vibration in the reverse direction, and thus it is possible to prevent from generating stress due to the pressure fluctuation when reducing the vibration. In addition, since the acoustic portion is provided along the outer surface of the vibration source, it is possible to achieve a relatively compact configuration.
- According to another aspect of the present invention in order to achieve the object, there is provided a combustor in which a combustion chamber is provided with the acoustic damper according to the above aspect and air vibration of combustion gas flowing in the combustion chamber is allowed to flow in the acoustic damper.
- According to the combustor, the pressure fluctuation in the combustor caused by combustion vibration is reduced by the acoustic portion. In addition, the exciting force generated by collision of the air vibration to the partition member when reducing the pressure fluctuation is suppressed with each other by each partition member serving as resistance of the air vibration in the reverse direction, and thus it is possible to prevent from generating stress on the combustor due to the pressure fluctuation when reducing the vibration. In addition, the acoustic portion is provided along the outer surface of the combustion chamber, and thus it is possible to achieve a relatively compact configuration of the combustor.
- In the combustor of the present invention, it is characterized that the passage is disposed along a circumferential direction of the combustion chamber.
- According to the combustor, it is possible to prevent from generating vibration displaced in the circumferential direction of the combustion chamber.
- In the combustor of the present invention, it is characterized that the passage is disposed along an axial direction of the combustion chamber.
- According to the combustor, it is possible to prevent from generating vibration displaced in the axial direction of the combustion chamber.
- According to still another aspect of the present invention in order to achieve the object, there is provided a gas turbine including the combustor according to the another aspect.
- According to the gas turbine, the combustion vibration generated in the combustor is reduced by the acoustic portion. For this reason, it is possible to reduce noise and vibration when driving the gas turbine. In addition, the exciting force generated by collision of the air vibration to the partition member when reducing the combustion vibration is suppressed with each other by each partition member serving as resistance of the air vibration in the reverse direction, it is possible to prevent from generating stress on the combustor due to the pressure fluctuation when reducing the vibration, and thus it is possible to prevent from generating stress on the gas turbine. In addition, the acoustic portion is provided along the outer surface of the combustion chamber, and thus it is possible to achieve a relatively compact configuration of the gas turbine with the combustor. Advantageous Effects of Invention
- According to the invention, it is possible to prevent from generating stress due to pressure fluctuation caused when reducing vibration, and to achieve a relatively compact configuration.
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FIG. 1 is a schematic diagram illustrating a configuration of a gas turbine according to an embodiment of the invention. -
FIG. 2 is a side view of a combustor according to the embodiment of the invention. -
FIG. 3 is a cross-sectional view illustrating an acoustic damper taken along the line A-A ofFIG. 2 according to the embodiment of the invention. -
FIG. 4 is a cross-sectional view taken along the line B-B ofFIG. 3 . -
FIG. 5 is a schematic diagram illustrating that the acoustic damper is developed in a circumferential direction. -
FIG. 6 is a schematic diagram illustrating that an acoustic damper compared with the acoustic damper according to the embodiment of the invention is developed in the circumferential direction. -
FIG. 7 is a diagram illustrating an influence based on the acoustic damper ofFIG. 6 . -
FIG. 8 is a diagram illustrating an influence based on the acoustic damper ofFIG. 6 . -
FIG. 9 is a schematic diagram illustrating that another unclaimed acoustic damper is developed in the circumferential direction. -
FIG. 10 is a schematic diagram illustrating that another unclaimed acoustic damper is developed in the circumferential direction. -
FIG. 11 is a cross-sectional view taken along the line A-A ofFIG. 2 and illustrating another unclaimed acoustic damper. -
FIG. 12 is a side view of a combustor illustrating another acoustic damper of the embodiment of the invention. - Hereinafter, an embodiment according to the invention will be described in detail with reference to the drawings. In addition, the invention is not limited to the embodiment. In addition, constituent elements in the embodiment to be described below include substantially the same elements of the elements which are replaceable and easy to understand by a person skilled in the art.
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FIG. 1 is a schematic diagram illustrating a configuration of a gas turbine according to the embodiment. As illustrated inFIG. 1 , the gas turbine includes acompressor 11, acombustor 12, aturbine 13, and aflue chamber 14, and thecompressor 11 is connected to a generator (not illustrated). Thecompressor 11 includes anair inlet 15 which brings the air in, and a plurality ofvanes 17 andblades 18 are alternately provided in acompressor cylinder 16. Thecombustor 12 supplies fuel to the air compressed by thecompressor 11, which is ignited by a burner to allow combustion. In theturbine 13, a plurality ofvanes 21 andblades 22 are alternately provided in aturbine cylinder 20. Theflue chamber 14 includes aflue diffuser 23 continuous to theturbine 13. In addition, arotor 24 is positioned to penetrate the center of thecompressor 11, thecombustor 12, theturbine 13, and theflue chamber 14, an end portion on thecompressor 11 side is rotatably supported by abearing portion 25, an end portion on theflue chamber 14 side is rotatably supported by abearing portion 26. A plurality of disc plates are fixed to therotor 24, and are connected to theblades compressor 11 side. - Accordingly, the air received from the
air inlet 15 of thecompressor 11 passes through the plurality ofvanes 17 andblades 18 and is compressed to be high-temperature and high-pressure compressed air, and predetermined fuel is supplied to the compressed air and is burned in thecombustor 12. The high-temperature and high-pressure combustion gas that is operation fluid generated by thecombustor 12 passes through the plurality ofvanes 21 andblades 22 constituting theturbine 13 to drive and rotate therotor 24 and drive the electric generator connected to therotor 24, and the flue gas is discharged to the air after conversion to positive pressure with theflue diffuser 23 of theflue chamber 14. -
FIG. 2 is a side view of the combustor according to the embodiment. Aninner cylinder 32 of thecombustor 12 is supported by the inside of acylinder housing 30 and anouter cylinder 31, a leading end of theinner cylinder 32 is connected to atransition piece 33 as the combustion chamber. - The
outer cylinder 31 is assembled with thecylinder housing 30. Theinner cylinder 32 is provided at a distance from the inside of theouter cylinder 31 to theouter cylinder 31, apilot nozzle 35 is provided along an axial direction that is an extending direction of a combustor axis S in the center portion therein. In addition, in theinner cylinder 32, a plurality ofmain nozzles 36 are provided in parallel to the combustor axis S to surround thepilot nozzle 35 along a circumferential direction on the inner circumferential face therein. In thetransition piece 33, a base end is cylindrically formed and is connected to the leading end of theinner cylinder 32, is curved and deformed while a cross section becomes smaller toward the leading end side, and the leading end is formed to be substantially rectangular and is opened toward thevane 21 at the first-stage of theturbine 13, and is assembled with thecylinder housing 30 through agusset 37. The inside of thetransition piece 33 is configured as a combustion room. In addition, the inside of thecylinder housing 30 is formed as acylinder 38, and thetransition piece 33 is provided in thecylinder 38. - In the
combustor 12, the high-temperature and high-pressure air from thecompressor 11 flows from the base end side of theinner cylinder 32 into theinner cylinder 32 through thecylinder 38. The compressed air is induced to thepilot nozzle 35 and themain nozzle 36. The compressed air is mixed with fuel ejected from themain nozzle 36 to be premixed gas, and the gas flows into thetransition piece 33. In addition, the compressed air is mixed with fuel ejected from thepilot nozzle 35, is ignited and burned by pilot light (not illustrated) to be combustion gas, and the gas is ejected into thetransition piece 33. In this case, a part of the flue gas is ejected to be diffused around with a flame in thetransition piece 33, and is ignited and burned in the premixed gas flowing from themain nozzles 36 into thetransition piece 33. That is, by the diffusion flame based on the pilot fuel ejected from thepilot nozzle 35, it is possible to perform flame holding for stable combustion of the dilute premixed fuel from themain nozzles 36. In addition, the fuel is premixed by themain nozzle 36 to make fuel concentration uniform, and thus it is possible to achieve lowering NOx. The flue gas is supplied to theturbine 13 through thetransition piece 33. -
FIG. 3 is a cross-sectional view taken along the line A-A ofFIG. 2 illustrating an acoustic damper according to the embodiment,FIG. 4 is a cross-sectional view taken along the line B-B ofFIG. 3 , andFIG. 5 is a schematic diagram illustrating that the acoustic damper is developed in a circumferential direction. - In the
combustor 12 of the gas turbine described above, vibration (combustion vibration) occurs when the fuel is burned. The combustion vibration causes noise or vibration when driving the gas turbine. Therein, the combustor 12 (the transition piece 33) as the vibration source in which the flue gas flows is provided with anacoustic damper 1A. - In
FIG. 2 , theacoustic damper 1A is provided along the circumferential direction on the outer surface on the base end side of thetransition piece 33 in thecombustor 12. As illustrated inFIG. 3 and FIG. 4 , theacoustic damper 1A includes ahousing 2 surrounding the outside of thetransition piece 33 as the vibration source. Thehousing 2 includes a cylindricalouter wall portion 2a surrounding the outside of thetransition piece 33 in the circumferential direction, and aside wall portion 2b fixed to thetransition piece 33 while closing both openings of theouter wall portion 2a, and forms an annular space on the outside of thetransition piece 33. In thetransition piece 33, a plurality of through-holes 33a allowing air vibration (pressure wave) V based on the combustion vibration in thetransition piece 33 to pass to the outside of thetransition piece 33 are formed in the circumferential direction of thetransition piece 33, at the portion where thehousing 2 is provided. - In addition, the
acoustic damper 1A includes acompartment wall 3 that partitions the space of thehousing 2 in the axial direction along theouter wall portion 2a, in thehousing 2. In addition, in thehousing 2, theacoustic damper 1A includes apartition wall 4 that partitions the space partitioned by thecompartment wall 3 into the inside and the outside in the space of thehousing 2. That is, thepartition wall 4 is provided between theouter wall portion 2a of thehousing 2 and the outer surface of thetransition piece 33. In addition, as illustrated inFIG. 3 , thepartition wall 4 is provided with anotch 4a communicating with the space of thehousing 2 partitioned into the inside and the outside at a part of the circumferential direction. One end of thepartition wall 4 notched by thenotch 4a in the circumferential direction is provided with apartition member 5a closing the outer space of thehousing 2. For this reason, the inner space of thehousing 2 communicates with the inside of thetransition piece 33 through the through-hole 33a of thetransition piece 33, the outer space of thehousing 2 is provided with an inlet communicating with the inner space of thehousing 2 by thenotch 4a, and an end portion taken along the circumferential direction forms a passage R blocked by thepartition member 5a. In addition, although each passage R is formed in the space of thehousing 2 partitioned in the axial direction by thecompartment wall 3, as illustrated inFIG. 5 , a configuration is achieved in which the inlet based on thenotch 4a and the end portion blocked by thepartition member 5a are inverted. - In addition, in the
acoustic damper 1A described above, onehousing 2 is partitioned in the axial direction by thecompartment wall 3 to configure two passages R, but two passages R may be configured by twohousings 2 without providing thecompartment wall 3. - In addition, a
partition member 5b is provided in the middle between the inlet and the end portion of each passage R. Thepartition member 5b blocks the middle of the passage R. In the passage R, the space between the inlet thereof and thepartition member 5b is configured as an acoustic portion N that reduces pressure fluctuation in thecombustor 12 in the passage R. In two passages R, the acoustic portion N is configured in which the positions of the inlet and thepartition member 5b in the circumferential direction are inverted. - In the
acoustic damper 1A configured as described above, as illustrated inFIG. 3 , when the fuel gas flows in thetransition piece 33, the air vibration (the pressure wave) V based on the combustion vibration of the combustion gas passes through the through-hole 33a of thetransition piece 33 and is received in thehousing 2. In the passage R, at the acoustic portion N between the inlet thereof and thepartition member 5b, the air vibration V propagating from the inlet resonates, and the pressure fluctuation in thecombustor 12 is reduced. In addition, as illustrated inFIG. 5 , in two passages R, the position in the circumferential direction between the inlet of each acoustic portion N and thepartition member 5b is inverted, and thus the propagation direction of the air vibration V becomes the reverse direction. - Herein,
FIG. 6 is a schematic diagram illustrating that an acoustic damper compared with the acoustic damper according to the embodiment is developed in the circumferential direction, andFIG. 7 and FIG. 8 are diagrams illustrating an influence based on the acoustic damper ofFIG. 6 . - In a
acoustic damper 100 illustrated inFIG. 6 , the number of an acoustic portion N of theacoustic damper 1A described is set to one. In theacoustic damper 100 with such a configuration, in pressure fluctuation in the acoustic portion N, acoustic pressure of the inlet portion is low, and is the maximum at thepartition member 5b. Meanwhile, between thepartition member 5b and thepartition member 5a, there is no propagation of the air vibration V, and acoustic pressure does not occur previously. In addition, thepartition member 5a is positioned at the inlet portion, and thus there is no large pressure fluctuation therein. For this reason, thepartition member 5b is subjected to very large pressure fluctuation on one face thereof, and is not subjected to the pressure fluctuation on the other face. As a result, since theacoustic damper 100 is subjected to the large pressure fluctuation on the face of the inlet side of thepartition member 5b, exciting force F toward the other face side of thepartition member 5b inFIG. 6 occurs. That is, the exciting force F in the circumferential direction occurs. -
- In the formula (1), fr denotes force of a radial direction component, fθ denotes force of a circumferential direction component, fz denotes force of an axial direction component, dr denotes vibration displacement in a radial direction, dθ denotes vibration displacement in a circumferential direction, and dz denotes vibration displacement in an axial direction.
- For example, in the
combustor 12 of the gas turbine described above, the leading end of thetransition piece 33 is assembled with thecylinder housing 30 through thegusset 37. In thegusset 37, asupport piece 37b extends above a substantiallyrectangular frame portion 37a of the leading end of thetransition piece 33, and thesupport piece 37b is assembled with thecylinder housing 30. In such atransition piece 33, when the exciting force F in the circumferential direction described above occurs, vibration in which the exciting force F rotates in the circumferential direction based on the assembled portion of thesupport piece 37b as a base point occurs. As a result, as illustrated inFIG. 7 , when the assembled portion of thesupport piece 37b is 0° and the bottom side of theframe portion 37a is 180°, as illustrated inFIG. 8 , in the circumferential displacement of thetransition piece 33, the 0° position supported by thegusset 37 is relatively slightly displaced, and the 180° position is drastically displaced. - Meanwhile, in the
acoustic damper 1A of the embodiment, the position of each acoustic portion N in the circumferential direction with respect to the inlet thereof and thepartition member 5b is inverted, and the propagation direction of the air vibration V is the reverse direction. For this reason, as illustrated inFIG. 5 , the exciting force F occurring at the position of eachpartition member 5b acts in the reverse direction with respect to each other. As a result, in thetransition piece 33 of thecombustor 12, the displacement occurring in the circumferential direction is suppressed. - The position of the
partition member 5b in the circumferential direction is a gap between thepartition member 5b and the inlet, and determines the length of the acoustic portion N. The length of the acoustic portion N is a distance for resonating the propagating air vibration V, and the distance is determined according to the frequency of the propagating air vibration V. That is, the position of thepartition member 5b in the circumferential direction is determined according to the frequency of the air vibration V that is a reducing target. In addition, since the acoustic pressure applied to thepartition member 5b by the position of the acoustic portion N in the axial direction is different, the position of thepartition member 5b in the circumferential direction is determined also considering the position of the acoustic portion N in the axial direction. In addition, when there is a possibility that each air vibration V reduced by each acoustic portion N resonates, the position of thepartition member 5b is determined also considering the possibility. The air vibration V and the transfer of the air vibration V in the acoustic portion N may be obtained by analysis such as Finit Element Method (FEM), and thus the position of thepartition member 5b in the circumferential direction may be determined such that the exciting force F of the formula (1) described above is 0. A distance between thepartition member 5b and thepartition member 5a is adjusted in length of the acoustic portion N that is a gap between thepartition member 5b and the inlet of the passage R. In addition, between thepartition member 5b and thepartition member 5a, theside wall portion 2b of thehousing 2 or thecompartment wall 3 may not be provided under the condition that the acoustic portion N is formed. - In addition, the
acoustic damper 1A illustrated inFIG. 5 is described in a form that two acoustic portions N are provided, but two or more acoustic portions N maybe provided, and the position of thepartition member 5b of each acoustic portion N may be set to suppress the exciting force F by the plurality of acoustic portions N. -
FIG. 9 and FIG. 10 are schematic diagrams illustrating that another acoustic damper is developed in the circumferential direction. Theacoustic damper 1A illustrated inFIG. 5 is provided with a plurality of acoustic portions N, but anacoustic damper 1B illustrated inFIG. 9 is provided with the acoustic portions N illustrated inFIG. 5 such that the passage R is folded in the reverse direction, and the folded portion is provided with anew partition member 5c and is configured as one passage. Accordingly, in the description of the followingacoustic damper 1B, the description of the same configuration as that of theacoustic damper 1A is not repeated. - Specifically, as illustrated in
FIG. 9 , theacoustic damper 1B is provided with thepartition member 5c in the middle of the passage R. Thepartition member 5c is provided continuously to the adjacent space partitioned by thecompartment wall 3. In the passage R, thecompartment wall 3 is opened at the portion of thepartition member 5c, and is configured by folding with thepartition member 5c. Thepartition member 5b as the end portion of the folded passage R is provided. As a result, the acoustic portion N is configured as one passage from the inlet (thenotch 4a) of the passage R to thepartition member 5b folded by thepartition member 5c. - In the
acoustic damper 1B, when the fuel gas flows into thetransition piece 33, the air vibration (the pressure wave) V based on the combustion vibration of the combustion gas passes through the through-hole 33a (seeFIG. 3 ) of thetransition piece 33 and is received in thehousing 2. In the passage R, at the acoustic portion N at the portion between the inlet and thepartition member 5c, the air vibration V propagating from the inlet resonates, and the pressure fluctuation in thecombustor 12 is reduced. In addition, at the acoustic portion N between thepartition member 5c and thepartition member 5b, the air vibration V propagating and folded by thepartition member 5c resonates, and the pressure fluctuation in thecombustor 12 is reduced. - In the
acoustic damper 1B, in the acoustic portion N, the propagating direction of the air vibration V is the reverse direction between the inlet and thepartition member 5c and between thepartition member 5c and thepartition member 5b. For this reason, as illustrated inFIG. 9 , the exciting force F occurring at the position of thepartition member 5c and the exciting force F occurring at the position of thepartition member 5b act in the reverse direction to each other. As a result, in thetransition piece 33 of thecombustor 12, the displacement occurring in the circumferential direction is suppressed. - The positions of the
partition member 5c and thepartition member 5b in the circumferential direction are a gap between thepartition member 5b and the inlet, and determine the length of the acoustic portion N. The length of the acoustic portion N is a distance for reducing the propagating air vibration V, and the distance is determined according to the frequency of the propagating air vibration V. That is, the positions of thepartition member 5c and thepartition member 5b in the circumferential direction are determined according to the frequency of the air vibration V that is the reducing target. The transfer of the air vibration V and the air vibration V in the acoustic portion N may be obtained by analysis such as Finit Element Method (FEM), and thus the positions of thepartition member 5c and thepartition member 5b in the circumferential direction may be determined such that the exciting force F of the formula (1) described above is 0. A distance between thepartition member 5c and thepartition member 5a (a distance between thepartition member 5c and thepartition member 5b) is adjusted in length of the acoustic portion N that is a gap between thepartition member 5b and the passage R. In addition, between thepartition member 5c and thepartition member 5a or between thepartition member 5c and thepartition member 5b, theside wall portion 2b of thehousing 2 or thecompartment wall 3 may not be provided under the condition that the acoustic portion N is formed. - In an
acoustic damper 1C illustrated inFIG. 10 , a plurality of acoustic portions N configured as one passage such as theacoustic damper 1B illustrated inFIG. 9 are disposed. - Specifically, as illustrated in
FIG. 10 , theacoustic damper 1C does not have thepartition member 5a of theacoustic damper 1B. For this reason, the number of passages R is two. Thepartition member 5c is formed in the middle of each passage R. Thepartition member 5c is provided continuously to the adjacent space partitioned by thecompartment wall 3. In each passage R, thecompartment wall 3 is opened at the portion of thepartition member 5c, and is configured by folding with thepartition member 5c. Thepartition member 5b as the end portion of the folded passage R is respectively provided. As a result, the acoustic portion N is configured as one passage from the inlet (thenotch 4a) of the passage R to thepartition member 5b folded by thepartition member 5c, and two passages are configured. - In each
acoustic damper 1C, when the fuel gas flows in thetransition piece 33, the air vibration (the pressure wave) V based on the combustion vibration of the fuel gas passes through the through-hole 33a (seeFIG. 3 ) of thetransition piece 33 and is received in thehousing 2. In the passage R, at the acoustic portion N at the portion between the inlet and thepartition member 5c, the air vibration V propagating from the inlet resonates, and the pressure fluctuation in thecombustor 12 is reduced. In addition, at the acoustic portion N between thepartition member 5c and thepartition member 5b, the air vibration V propagating and folded by thepartition member 5c resonates, and the pressure fluctuation in thecombustor 12 is reduced. - In the
acoustic damper 1C, in each acoustic portion N, the propagating direction of the air vibration V is the reverse direction between the inlet and thepartition member 5c and between thepartition member 5c and thepartition member 5b. For this reason, as illustrated inFIG. 10 , in each acoustic portion N, the exciting force F occurring at the positions of thepartition member 5c and the exciting force F occurring at the position of thepartition member 5b act in the reverse direction to each other. As a result, in thetransition piece 33 of thecombustor 12, the displacement occurring in the circumferential direction is suppressed. - The positions of the
partition member 5c and thepartition member 5b in the circumferential direction are a gap between thepartition member 5b and the inlet, and determine the length of the acoustic portion N. The length of the acoustic portion N is a distance for reducing the propagating air vibration V, and the distance is determined according to the frequency of the propagating air vibration V. That is, the positions of thepartition member 5c and thepartition member 5b in the circumferential direction are determined according to the frequency of the air vibration V that is the reducing target. Theacoustic damper 1C includes two acoustic portions N, and thus it is possible to reduce the air vibration V according to the frequency of the plurality of air vibration V by changing each length. In addition, when there is a possibility that each air vibration V reduced by each acoustic portion N resonates, the position of thepartition member 5b is determined also considering the possibility. The transfer of the air vibration V and the air vibration V in the acoustic portion N may be obtained by analysis such as Finit Element Method (FEM), and thus the positions of thepartition member 5c and thepartition member 5b in the circumferential direction may be determined such that the exciting force F of the formula (1) described above is 0. A distance between eachpartition member 5c and eachpartition member 5b is adjusted in length of the acoustic portion N that is a gap between thepartition member 5b and the inlet of the passage R. In addition, between eachpartition member 5c and eachpartition member 5b, theside wall portion 2b of thehousing 2 or thecompartment wall 3 may not be provided under the condition that the acoustic portion N is formed. - In addition, in
FIG. 10 , theacoustic damper 1C represents one folding of the acoustic portion N, but the folding is not limited to one. Although not illustrated in the drawings, in each acoustic portion, as a plurality of folding, each folded portion may be provided with thepartition member 5c. -
FIG. 11 is a cross-sectional view taken along the line A-A ofFIG. 2 and illustrating another acoustic damper. In theacoustic dampers transition piece 33 that is the extending direction of the combustor axis S, but the acoustic portion N may be folded and provided in the radial direction of the combustor axis S on the outer surface of thetransition piece 33, as in anacoustic damper 1D illustrated inFIG. 11 . - In the
acoustic damper 1D illustrated inFIG. 11 , ahousing 2 includes an cylindricalouter wall portion 2a (not illustrated) surrounding the outside of thetransition piece 33 in the circumferential direction, similarly to theacoustic dampers partition walls 6 are provided on the outside in the radial direction of thepartition wall 4 between theouter wall portions 2a, the circumferential direction between thepartition wall 4 and thepartition wall 6 and between thepartition walls 6 is closed by apartition member 5d to form a plurality of spaces overlapped with the radial direction, and each space is configured to form one passage R folded and connected in the radial direction by thepartition member 5d. Thenotch 4a as the inlet of the passage R is provided at the position of thepartition member 5d on the inside in the most radial direction of the passage R, to configure the acoustic portion N. - As illustrated in
FIG. 11 , in theacoustic damper 1D configured as described above, when the fuel gas flows in thetransition piece 33, the air vibration (the pressure wave) V based on the combustion vibration of the combustion gas passes through the through-hole 33a of thetransition piece 33 and is received in thehousing 2. In the passage R, at the acoustic portion N between the inlet thereof and thepartition member 5d of the end portion of the passage R, the air vibration V propagating from the inlet resonates, and the pressure fluctuation in thecombustor 12 is reduced. In addition, the air vibration folded and propagating by thepartition member 5d resonates, and the pressure fluctuation in thecombustor 12 is reduced. - In the
acoustic damper 1D, in the acoustic portion N, the propagating direction of the air vibration V is the reverse direction between thepartition members 5d. For this reason, as illustrated inFIG. 11 , the exciting force F occurring at the position of thepartition member 5d on one direction side of the circumferential direction and the exciting force F occurring at the position of thepartition member 5b on the other direction side of the circumferential direction act in the reverse direction to each other. As a result, in thetransition piece 33 of thecombustor 12, the displacement occurring in the circumferential direction is suppressed. - The position of the
partition member 5d in the circumferential direction is a gap between thepartition member 5b of the end portion and the inlet, and determines the length of the acoustic portion N. The length of the acoustic portion N is a distance for reducing the propagating air vibration V, and the distance is determined according to the frequency of the propagating air vibration V. That is, the position in the circumferential direction of thepartition member 5d closing the circumferential direction between thepartition wall 4 and thepartition wall 6 and between thepartition walls 6 is determined according to the frequency of the air vibration V that is the reducing target. The transfer of the air vibration V and the air vibration V in the acoustic portion N may be obtained by analysis such as Finit Element Method (FEM), and thus the position of thepartition member 5d in the circumferential direction may be determined such that the exciting force F of the formula (1) described above is 0. - In addition, as illustrated in
FIG. 11 , in theacoustic damper 1D, a plurality (three in the embodiment) of acoustic portions N configured in the same manner are disposed in the circumferential direction. That is, theacoustic damper 1D includes the plurality of acoustic portions N, and thus it is possible to reduce the air vibration V according to the frequency of the plurality of air vibration V by changing each length. In addition, when there is a possibility that each air vibration V reduced by each acoustic portion N resonates, the position of thepartition member 5d is determined also considering the possibility. - In addition, as illustrated in
FIG. 11 , theacoustic damper 1D is provided with thepartition member 5c at each folded portion of each passage R in two acoustic portions disposed at the lower portion ofFIG. 11 . -
FIG. 12 is a side view of a combustor illustrating another acoustic damper of the embodiment. Theacoustic dampers transition piece 33, but as illustrated inFIG. 12 , theacoustic dampers transition piece 33 that is the extending direction of the combustor axis S on the outer surface of thetransition piece 33. According to theacoustic dampers FIG. 12 , it is possible to reduce the air vibration V, and to prevent from generating stress in the axial direction with the reducing. In addition, theacoustic dampers transition piece 33 and the axial direction. - As described above, the acoustic dampers (1A, 1B, 1C, and 1D) of the embodiment are fixed to the vibration source (the combustor 12) to be provided along the outer surface of the vibration source, form the passage R that takes in the air vibration V generated by the vibration source, and are provided with the acoustic portion N having the
partition members - The acoustic dampers (1A, 1B, 1C, and 1D) reduce the pressure fluctuation in the vibration source (the combustor 12) by the acoustic portion N. In addition, the exciting force F generated by collision of the air vibration V to the
partition members partition member 5b (5c) and 5d serving as resistance of the air vibration V in the reverse direction, and thus it is possible to prevent from generating stress due to the pressure fluctuation when reducing the vibration. In addition, in the acoustic dampers (1A, 1B, 1C, and 1D), the acoustic portion N is provided along the outer surface of the vibration source, and thus it is possible to configure the acoustic dampers (1A, 1B, 1C, and 1D) in a relatively compact size. - In the acoustic dampers (1B, 1C, and 1D) of the embodiment, the acoustic portion N is provided in which the passage R is folded in the reverse direction, and the
partition members - The acoustic dampers (1B, 1C, and 1D) reduce the pressure fluctuation in the vibration source (the combustor 12) by the acoustic portion N. In addition, the exciting force F generated by collision of the air vibration V to the
partition members partition member - In addition, in the acoustic dampers (1C and 1D) of the embodiment, a plurality of acoustic portions N configured by folding the passage R are disposed.
- The acoustic dampers (1C and 1D) reduce the pressure fluctuation in the vibration source (the combustor 12) by the acoustic portion N. In addition, the exciting force F generated by collision of the air vibration V to the
partition members partition member acoustic dampers - In the acoustic dampers (1B, 1C, and 1D) of the embodiment, the folding of the passage R is performed a plurality of times, and the
partition member 5c is provided at each folded portion. - The acoustic dampers (1B, 1C, and 1D) reduce the pressure fluctuation in the vibration source (the combustor 12) by the acoustic portion N. In addition, the exciting force F generated by collision of the air vibration V to the
partition members partition member - In addition, in the
combustor 12 of the embodiment, the combustion chamber (the transition piece 33) is provided with any one acoustic damper (1A, 1B, 1C, and 1D) described above, and the air vibration V of the combustion gas flowing in the combustion chamber is allowed to flow in the acoustic damper. - According to the
combustor 12, the pressure fluctuation in thecombustor 12 based on the combustion vibration is reduced by the acoustic portion N. In addition, the exciting force F generated by collision of the air vibration V to thepartition members partition member 5b (5c) and 5d serving as resistance of the air vibration V in the reverse direction, and thus it is possible to prevent from generating stress on thecombustor 12 due to the pressure fluctuation when reducing the vibration. In addition, in thecombustor 12, the acoustic portion N is provided along the outer surface of the combustion chamber, and thus it is possible to configure thecombustor 12 in a relatively compact size. - In addition, in the
combustor 12 of the embodiment, the passage R is disposed along the circumferential direction of the combustion chamber (the transition piece 33). - According to the
combustor 12, it is possible to prevent generation of vibration displaced in the circumferential direction of the combustion chamber (the transition piece 33). - In addition, in the
combustor 12 of the embodiment, the passage R is disposed along the axial direction of the combustion chamber (the transition piece 33). - According to the
combustor 12, it is possible to prevent generation of vibration displaced in the axial direction of the combustion chamber (the transition piece 33). - The gas turbine of the embodiment is provided with any one
combustor 12 described above. - According to the gas turbine, the combustion vibration occurring in the
combustor 12 is reduced by the acoustic portion N. For this reason, it is possible to reduce noise or vibration when driving the gas turbine. In addition, the exciting force F generated by collision of the air vibration V to thepartition members partition member 5b (5c) and 5d serving as resistance of the air vibration V in the reverse direction, generation of stress on thecombustor 12 due to the pressure fluctuation when reducing the vibration is prevented, and thus it is possible to prevent from generating stress on the gas turbine. In addition, in the gas turbine, the acoustic portion N is provided along the outer surface of the combustion chamber (the transition piece 33), and it is possible to configure the gas turbine in a relatively compact size, with thecombustor 12. Reference Signs List -
- 1A, 1B, 1C, 1D
- ACOUSTIC DAMPER
- 2
- HOUSING
- 2a
- OUTER WALL PORTION
- 2b
- SIDE WALL PORTION
- 3
- COMPARTMENT WALL
- 4, 6
- PARTITION WALL
- 4a
- NOTCH
- 5a, 5b, 5c, 5d
- PARTITION MEMBER
- 12
- COMBUSTOR
- 33
- TRANSITION PIECE (COMBUSTION CHAMBER)
- 33a
- THROUGH-HOLE
- 37
- GUSSET
- 37a
- FRAME PORTION
- 37b
- SUPPORT PIECE
- F
- EXCITING FORCE
- M
- ACOUSTIC PORTION
- R
- PASSAGE
- S
- COMBUSTOR AXIS
- V
- AIR VIBRATION
Claims (5)
- An acoustic damper (1A, 1B, 1C) fixed to a vibration source along an outer surface of the vibration source which, in operation, generates air vibration (V), the acoustic damper (1A, 1B, 1C) comprising:a housing (2) surrounding the outside of the outer surface of the vibration source so as to form a space on the outside of the outer surface, wherein a plurality of through holes (33a) are formed in the circumferential direction of the vibration source at the portion where the housing (2) is provided that allow air vibration (V) to pass to the outside of the vibration source and into the space; characterised by :a compartment wall (3) arranged in the housing (2) so as to partition the space formed by the housing (2) in an axial direction along an outer wall portion (2a) of the housing to form two adjacent passages (R) that takes in air vibration (V) generated by the vibration source;a partition wall (4) arranged so as to respectively further partition the adjacent passages (R) into an inner space adjacent the outer surface of the vibration source and an outer space remote from the outer surface of the vibration source,wherein each outer space is respectively provided with an inlet (4a) communicating with the inner space, with a first partition member (5a) forming an end portion of the passage (R), and with a second partition member (5b) serving as resistance against the air vibration (V), and closing a downstream side of the passage (R) with respect to a propagation direction of the air vibration (V) in an acoustic portion (N) configured as the space from the inlet (4a) at the end portion along the direction of the passage (R) to the second partition member (5b),wherein the inlet (4a) and the first and second partition members (5a,5b) are arranged such that the propagation directions of the air vibration (V) in the adjacent passages (R) are reversed to each other.
- A combustor (12) in which a combustion chamber (33) is provided with the acoustic damper (1A) according to claim 1 fixed along an outer surface of the combustion chamber (33) as the vibration source such that air vibration (V) of combustion gas flowing in the combustion chamber (33) is allowed to flow in the acoustic damper (1A).
- The combustor (12) according to claim 2, wherein the acoustic damper (1A) is provided such that the passages (R) are disposed along a circumferential direction of the , combustion chamber (33).
- The combustor (12) according to claim 2, wherein the acoustic damper (1A) is provided such that the passages (R) are disposed along an axial direction of the combustion chamber (33).
- A gas turbine comprising the combustor (12) according to any one of claims 2 to 4.
Priority Applications (1)
Application Number | Priority Date | Filing Date | Title |
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EP15156023.2A EP2930429B1 (en) | 2011-03-22 | 2012-02-20 | Acoustic damper, combustor, and gas turbine |
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JP2011063298 | 2011-03-22 | ||
PCT/JP2012/053988 WO2012127959A1 (en) | 2011-03-22 | 2012-02-20 | Acoustic damper, combustor, and gas turbine |
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EP15156023.2A Division EP2930429B1 (en) | 2011-03-22 | 2012-02-20 | Acoustic damper, combustor, and gas turbine |
EP15156023.2A Division-Into EP2930429B1 (en) | 2011-03-22 | 2012-02-20 | Acoustic damper, combustor, and gas turbine |
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EP2690365A1 EP2690365A1 (en) | 2014-01-29 |
EP2690365A4 EP2690365A4 (en) | 2014-08-27 |
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EP15156023.2A Active EP2930429B1 (en) | 2011-03-22 | 2012-02-20 | Acoustic damper, combustor, and gas turbine |
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EP (2) | EP2690365B1 (en) |
JP (3) | JP5623627B2 (en) |
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2012
- 2012-02-20 EP EP12760742.2A patent/EP2690365B1/en active Active
- 2012-02-20 WO PCT/JP2012/053988 patent/WO2012127959A1/en active Application Filing
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JP2014130009A (en) | 2014-07-10 |
US20130206500A1 (en) | 2013-08-15 |
JP5623627B2 (en) | 2014-11-12 |
EP2930429B1 (en) | 2016-12-14 |
CN103140716A (en) | 2013-06-05 |
EP2690365A1 (en) | 2014-01-29 |
EP2930429A1 (en) | 2015-10-14 |
KR20130101041A (en) | 2013-09-12 |
US8733496B2 (en) | 2014-05-27 |
EP2690365A4 (en) | 2014-08-27 |
JP5995932B2 (en) | 2016-09-21 |
KR101498400B1 (en) | 2015-03-30 |
JP2014238099A (en) | 2014-12-18 |
WO2012127959A1 (en) | 2012-09-27 |
JPWO2012127959A1 (en) | 2014-07-24 |
CN103140716B (en) | 2015-05-27 |
JP5813169B2 (en) | 2015-11-17 |
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